CN114855106A - Local heat treatment device and method for large-scale complex aviation titanium alloy structural part after repair - Google Patents
Local heat treatment device and method for large-scale complex aviation titanium alloy structural part after repair Download PDFInfo
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- CN114855106A CN114855106A CN202210385607.0A CN202210385607A CN114855106A CN 114855106 A CN114855106 A CN 114855106A CN 202210385607 A CN202210385607 A CN 202210385607A CN 114855106 A CN114855106 A CN 114855106A
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Abstract
The invention discloses a local heat treatment device and a local heat treatment method for an aviation titanium alloy large-scale complex structural part after repair, wherein the local heat treatment device for the aviation titanium alloy large-scale complex structural part after repair comprises the following steps: the heater is used for attaching and heating the repair part of the large complex aviation titanium alloy structural part; the temperature sensor is used for detecting the temperature of the repair part of the large complex aviation titanium alloy structural part; and the temperature controller is respectively in communication connection with the heater and the temperature sensor. According to the scheme, the repair part of the large-scale complex aviation titanium alloy structural part can be effectively subjected to local heat treatment, the size of a heat treatment device can be greatly reduced, and the condition that the repair workpiece is deformed by heating to cause out-of-tolerance can be prevented.
Description
Technical Field
The invention relates to the technical field of local heat treatment after repair of large complex aviation titanium alloy structural components, in particular to a device and a method for local heat treatment after repair of large complex aviation titanium alloy structural components.
Background
The working environment of large-scale complex structural members of aviation titanium alloy such as a casing, a blisk and the like is a high-temperature and high-pressure environment, and damage failure conditions such as cracks, corrosion, abrasion and the like are inevitable in the service process. The rapid repair of the damaged part is realized by adopting high-energy beam repair processes such as laser additive repair, electron beam welding and the like, and the method has great economic benefit for prolonging the service life of the damaged part. The high-energy beam repairing process has the characteristic of rapid fusing, so that the tissue of the repaired part is a metastable tissue, and a repaired structural part inevitably has large residual stress, which directly influences the mechanical property of the repaired part.
The heat treatment is a main process means and an essential procedure for realizing the elimination of residual stress and the regulation and control of the organization of the repair area of the large-scale complex structural component of the aviation titanium alloy and further improving the mechanical property of the repair component. The large complex structural part of aviation titanium alloy belongs to large thin-wall parts, the whole heat treatment needs vacuum furnace equipment with larger size and heat treatment clamps with complex structures, and the stress release during the whole heat treatment of the workpiece is easy to cause new deformation out of tolerance.
Disclosure of Invention
In view of the above, the invention provides a local heat treatment device for repaired large complex aviation titanium alloy structural parts, which can effectively perform local heat treatment on repaired parts of the large complex aviation titanium alloy structural parts, not only can greatly reduce the size of the heat treatment device, but also can prevent the repaired workpiece from being out of tolerance caused by thermal deformation.
In order to achieve the purpose, the invention provides the following technical scheme:
a local heat treatment device for large-scale complex structural parts of aviation titanium alloy comprises:
the heater is used for heating the repair part of the large-scale complex aviation titanium alloy structural part in a fitting manner;
the temperature sensor is used for detecting the temperature of the repair part of the large-scale complex aviation titanium alloy structural part;
and the temperature controller is respectively in communication connection with the heater and the temperature sensor.
Preferably, the heater is a flexible heater.
Preferably, the flexible heater comprises a caterpillar ceramic heater or a silicone rubber flexible heater.
Preferably, the temperature sensor includes:
the thermocouple is arranged on the surface of the repair part of the large-scale complex aviation titanium alloy structural part;
the heater is attached to the surface of the repair part of the large complex aviation titanium alloy structural part and wraps the thermocouple.
Preferably, the number of the thermocouples is two, and the thermocouples are temperature measuring thermocouples and temperature control thermocouples respectively;
the temperature thermocouple and the temperature thermocouple are arranged on different surfaces of the repair part of the large complex aviation titanium alloy structural part and are in one-to-one communication connection with two different interfaces of the temperature controller, so that the detection value of the temperature thermocouple is larger than that of the temperature thermocouple.
Preferably, the method further comprises the following steps:
and the heat insulation layer is used for wrapping the repair part of the large-scale complex aviation titanium alloy structural part and is positioned on the outer side of the heater.
Preferably, the insulation layer comprises an asbestos insulation layer.
Preferably, the method further comprises the following steps:
and the argon protection box is used for placing the large-scale complex structural part of the aviation titanium alloy, and the heater and the temperature sensor are both positioned in the argon protection box.
The local heat treatment method after the repair of the large complex aviation titanium alloy structural part adopts the local heat treatment device for local heat treatment after the repair of the large complex aviation titanium alloy structural part, and comprises the following steps:
s1, setting temperature rise time, heat preservation temperature, heat preservation time and cooling time of each stage of local heat treatment through a temperature controller according to the determined heat treatment schedule of the large complex aviation titanium alloy structural part;
and S2, controlling the operation of the heater through a temperature controller according to the temperature rise time, the heat preservation temperature and the heat preservation time of each stage of the local heat treatment set in the step S1.
Preferably, in step S1, the heat treatment schedule for the large complex structural component made of the aviation titanium alloy includes:
uniformly heating to 600 ℃ in multiple stages according to a preset heating speed, and keeping the temperature for 4 hours; and keeping the temperature for 5min when the temperature is raised to the corresponding preset temperature in each stage.
According to the technical scheme, the local heat treatment device for the repaired large-scale complex aviation titanium alloy structural part can effectively carry out local heat treatment on the repaired part of the large-scale complex aviation titanium alloy structural part, not only can the size of the heat treatment device be greatly reduced, but also the repaired workpiece can be prevented from being out of tolerance caused by thermal deformation.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a local heat treatment device after repair of a large complex aviation titanium alloy structural part according to an embodiment of the present invention;
FIG. 2 is a schematic installation diagram of a heating device for a heat treatment area after repair of a large complex aviation titanium alloy structural part according to an embodiment of the invention;
fig. 3 is a schematic view of the installation of the flexible heater and the asbestos insulation layer provided by the embodiment of the invention.
Wherein, 1 is an argon protection box; 2 is a thermocouple; 3 is a flexible heater; 4, an aviation titanium alloy large-scale complex structural part; 5 is a temperature controller; 6 is a repair area; 7 is an asbestos heat-insulating layer.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The local heat treatment device for the repaired large-scale complex aviation titanium alloy structural part, as shown in fig. 1, comprises:
the heater is used for heating the repair part of the large-scale complex aviation titanium alloy structural part 4 in a fitting manner;
the temperature sensor is used for detecting the temperature of the repair part of the large-scale complex structural component 4 of the aviation titanium alloy;
and the temperature controller 5 is respectively in communication connection with the heater and the temperature sensor.
It should be noted that the heating temperature of the heater can be fed back by the temperature sensor; of course, the temperature controller 5 controls the operation of the heater according to the detection value of the temperature sensor. For example, when the large complex aviation titanium alloy structural component 4 is heated to a corresponding preset temperature at a certain stage, the temperature controller 5 controls the heater to enter a heat preservation state according to the feedback of the temperature sensor. That is to say, the temperature controller 5 of this scheme realizes the accurate regulation and control to heater heating temperature according to temperature sensor's detection feedback. In addition, the local heat treatment device provided by the scheme is suitable for large-scale complex structural parts of aviation titanium alloy such as engine casings and blisks, and is also suitable for titanium alloy shells of spacecrafts, fuel storage boxes and the like. In addition, the large complex structural component 4 of the aviation titanium alloy in fig. 1 is an engine case.
According to the technical scheme, the local heat treatment device for the repaired large-scale complex aviation titanium alloy structural component provided by the embodiment of the invention can effectively perform local heat treatment on the repaired part of the large-scale complex aviation titanium alloy structural component, so that the size of the heat treatment device can be greatly reduced, a heat treatment clamp with a complex structure is prevented from being designed and manufactured, and the out-of-tolerance caused by thermal deformation of a repaired workpiece can be prevented.
In this embodiment, the heater is a flexible heater 3, as shown in fig. 2. That is to say, the heater of this scheme adopts flexible heater 3 to in the structural feature according to restoreing work piece repair position carries out laminating flexible heating, thereby can help promoting the local heat treatment effect of restoreing the work piece, make the heat affected zone of restoreing the work piece repair position little, the deformation is little.
Specifically, the flexible heater 3 includes a caterpillar ceramic heater or a silicon rubber flexible heater. The flexible heater 3 adopts a crawler-type ceramic heater, can be spliced, bent or wound, attached and heated according to the structural characteristics of the repaired part of the repaired workpiece, and can realize adaptive contact heating on the repaired part of the repaired workpiece, so that a simple and effective heating mode can be provided for repairing the complex structure of the repaired area of the workpiece.
Further, as shown in fig. 2, the temperature sensor includes:
the thermocouple 2 is arranged on the surface of the repair part of the large-scale complex aviation titanium alloy structural part 4;
the heater is attached to the surface of the repair part of the large-scale complex aviation titanium alloy structural part 4 and wraps the thermocouple 2. That is, as shown in fig. 2, the heater is attached to the surface of the repair part of the large complex aircraft titanium alloy structural member 4, and the thermocouple 2 is installed inside the heater. The design so that this scheme to make thermocouple 2's temperature detection more accurate, thereby help promoting this device local thermal treatment's accuracy.
Still further, as shown in fig. 2, the number of the thermocouples 2 is two, and the thermocouples are temperature measuring thermocouples and temperature controlling thermocouples respectively; of course, the heater wraps the temperature thermocouple and the temperature thermocouple;
the temperature thermocouple and the temperature control thermocouple are arranged on the different surfaces of the repaired part of the large complex structural component 4 made of the aviation titanium alloy and are in one-to-one corresponding communication connection with two different interfaces of the temperature controller 5, so that the detection value of the temperature control thermocouple is larger than that of the temperature thermocouple, namely, the temperature value of the temperature control thermocouple at the same repaired part is not lower than that of the temperature measurement thermocouple, and accurate regulation and control of heating temperature are guaranteed.
Further, the temperature controller 5 is provided with 6 interfaces which are respectively No. 1, No. 2, No. 3, No. 4, No. 5 and No. 6 interfaces; the interfaces 1, 2 and 3 are used for being in communication connection with the temperature control thermocouples respectively, the interfaces 4, 5 and 6 are used for being in communication connection with the temperature measurement thermocouples respectively, and the temperature controller 5 can display the numerical value of each thermocouple 2 connected with the temperature controller, so that the temperature values of the two thermocouples 2 at the heat treatment positions of the repaired workpiece can be seen. In addition, before the heat treatment, the temperature of the temperature-controlling thermocouple and the temperature-measuring thermocouple was detected by preheating the heat treatment site:
taking a first temperature control thermocouple (which is in communication connection with the interface No. 1) and a first temperature thermocouple (which is in communication connection with the interface No. 4) as an example for explanation, if the temperature of the first temperature control thermocouple is higher than that of the first temperature thermocouple, the temperature of a heating area can be ensured to reach the temperature set by heat treatment; if the temperature of the first temperature control thermocouple is lower than that of the first temperature measuring thermocouple, the power lines of the No. 1 interface and the No. 4 interface are connected in a switching mode, and therefore the temperature of the first temperature control thermocouple is higher than that of the first temperature measuring thermocouple. That is, if it is not guaranteed that the temperature of the temperature-controlling thermocouple is greater than the temperature-measuring thermocouple, the temperature of the heat-treated area may not reach the set value.
That is to say, this scheme is based on the multiple spot thermocouple optimal arrangement and real-time temperature measurement, and the heating power of automatic regulation and control heater guarantees local heating temperature accessibility, guarantees to reach the reliability of required heat treatment system, can realize the adaptability local heat treatment of the repair structure of polymorphic type damage.
In the scheme, in order to improve the heat preservation effect of the repaired workpiece in the local heat treatment; correspondingly, the local heat treatment device for the repaired large-scale complex aviation titanium alloy structural part provided by the embodiment of the invention further comprises:
the heat insulation layer is used for wrapping the repair part of the large-scale complex aviation titanium alloy structural part 4 and is positioned on the outer side of the heater. That is, as shown in fig. 2 and 3, the heater first wraps and fixes the thermocouple in the heat treatment area (repair part, i.e., repair area 6 of the large complex structural component of the aviation titanium alloy) of the large complex structural component of the aviation titanium alloy, and then the outer layer of the heater is wrapped and fixed by the heat insulation layer. Therefore, better heat preservation effect and temperature control effect can be obtained.
Specifically, as shown in fig. 3, the insulation layer includes an asbestos insulation layer 7. Wherein, asbestos heat preservation 7 has the characteristics such as effectual, the simple installation of heat preservation, long service life.
In order to further optimize the above technical solution, as shown in fig. 1, the local heat treatment apparatus for the large complex structural component of the aviation titanium alloy according to the embodiment of the present invention further includes:
the argon protection box 1 is used for placing the large complex aviation titanium alloy structural part 4, and the heater and the temperature sensor are both positioned in the argon protection box. That is to say, the scheme provides the argon protection box 1 so as to provide a low-water-oxygen and argon-protected heat treatment environment for local heat treatment of the repaired workpiece; wherein, the water oxygen content in the box can be lower than 50PPM after purification, thereby effectively preventing the repair workpiece from high-temperature oxidation during local heat treatment.
The embodiment of the invention also provides a local heat treatment method after the repair of the large complex structural part of the aviation titanium alloy, which adopts the local heat treatment device after the repair of the large complex structural part of the aviation titanium alloy to carry out local heat treatment and comprises the following steps:
s1, setting temperature rise time, heat preservation temperature, heat preservation time and cooling time of each stage of local heat treatment through a temperature controller according to the determined heat treatment system after repairing the large-scale complex aviation titanium alloy structural part;
and S2, controlling the operation of the heater through a temperature controller according to the temperature rise time, the heat preservation temperature and the heat preservation time of each stage of the local heat treatment set in the step S1.
It should be noted that the time of the different processes in each stage can be set by the temperature controller, so that the time of the different processes in each stage can be accurately controlled. In addition, the heater (flexible heater) in the scheme adopts high frequency with the frequency of 20-80kHz for heating, so that the local heat treatment effect of the repaired workpiece is ensured; in addition, the current of the heater is adjusted through the temperature controller, and the output power of the heater is controlled. Meanwhile, the local heat treatment device for the repaired large-scale complex aviation titanium alloy structural part has corresponding beneficial effects because the local heat treatment device is used for carrying out local heat treatment after the repair of the large-scale complex aviation titanium alloy structural part, and specific reference can be made to the previous description, and the description is omitted.
In the scheme, in order to obtain a better local heat treatment effect on the repaired workpiece; correspondingly, in step S1, the post-repair heat treatment system for the large complex aviation titanium alloy structural component includes:
uniformly heating to 600 ℃ in multiple stages according to a preset heating speed, and keeping the temperature for 4 hours; and keeping the temperature for 5min when the temperature is raised to the corresponding preset temperature in each stage. Further, the preset temperature-rising speed may be 100 ℃/10 min.
The present solution is further described below with reference to specific embodiments:
the invention adopts flexible heating local heat treatment to effectively solve the problems in the background art, and the flexible heating only heats the repaired part, and the heating speed, the temperature and the range are controllable. The adaptability of the flexible heater and the accuracy of the regulation and control of the heat treatment schedule directly determine the effects of stress release and tissue regulation and control. Therefore, the key of the flexible local heat treatment is how to carry out the precise control of the design of the flexible heater and the regulation and control of the heat treatment schedule according to the structural characteristics of the repair part of the large-scale complex aviation titanium alloy structural component.
The invention aims to provide a local heat treatment method for repaired large complex aviation titanium alloy structural parts, which can accurately perform local heat treatment on the repaired parts of the large complex aviation titanium alloy structural parts on the premise of preventing high-temperature oxidation during local heat treatment and preventing the thermal deformation of repaired workpieces from being out of tolerance, so that the residual stress is reduced, and the structure and the mechanical property are improved.
A local heat treatment method for an aviation titanium alloy large-scale complex structural part after repair comprises the following steps: argon gas guard box and intelligent temperature controller, characterized by: argon gas guard box inside place the local thermal treatment structure of flexible heating, the local thermal treatment structure of flexible heating include the asbestos heat preservation, asbestos heat preservation internally mounted crawler-type ceramic heater, installation crawler-type ceramic heater internally mounted flexible thermocouple, the thermocouple pass through the outer intelligent temperature controller of transmission line and inert gas guard box and link to each other, crawler-type ceramic heater be fixed in the large-scale complicated structural component heat treatment area of aviation titanium alloy with flexible thermocouple parcel, the asbestos heat preservation will crawler-type ceramic heater skin parcel fixed, the argon gas guard box from taking clean system, and side-mounting argon gas intake pipe.
The local heat treatment method for the repaired large-scale complex aviation titanium alloy structural part comprises the following steps:
1. a flexible heater design. The flexible heater adopted by the invention is a crawler-type ceramic heater, and the matched flexible heater is designed by combining the structural characteristics of a long-strip-shaped repair area and an annular repair area thereof aiming at the structural characteristics of the repair part of the large-scale complex aviation titanium alloy structural component; for a strip-shaped repair area (as shown in fig. 2), the length of the flexible heater is 0.5-1 cm greater than that of the whole repair area, and the whole width of the flexible heater is 3-5 cm greater than that of the repair area, so that the heating area of the repair area is ensured; for the annular repairing area, the whole length of the flexible heater is equal to the perimeter of the annular repairing area, the whole width of the flexible heater is 3-5 cm larger than that of the repairing area, and the design scheme realizes accurate control of the heating area on the premise of ensuring the adaptability of the flexible heater;
2. placing the large complex aviation titanium alloy structural part in an argon protection box;
3. and (4) determining a heat treatment system. The large complex aviation titanium alloy structural part is made of titanium alloy, and the repair mode of the large complex aviation titanium alloy structural part generally adopts processes such as electron beam welding, laser additive repair and the like; after the large complex aviation titanium alloy structural part is repaired, the residual stress of a repair area is large; according to the characteristics of the repaired tissue, adopting a stress relief annealing heat treatment process; the heat treatment system of the stress relief annealing of the titanium alloy is 600 ℃, and the temperature is kept for 4 hours; before the temperature rises to 600 ℃: heating up to 100 deg.C/10 min each time, and keeping the temperature for 5 min; keeping the temperature for 4 hours after the temperature reaches 600 ℃; after the heat preservation time is over, naturally cooling the argon protection box;
4. thermocouple clamping and temperature monitoring. Selecting a right and straight thermocouple with proper length, installing 2 thermocouples at each repair area and ensuring that the thermocouples cannot be loosened, wherein the functions of the thermocouples are temperature control and temperature measurement respectively; before local heat treatment, preliminarily setting the temperature rise temperature to be 150 ℃ and the temperature rise time to be 5min by an intelligent temperature controller, adjusting the current control output power, checking the temperature of a thermocouple in a temperature control area and a thermocouple in a temperature measurement area after the temperature rise time is reached, if the temperature value of the temperature control thermocouple is not lower than that of the temperature measurement thermocouple, not adjusting the connection, if the temperature value of the temperature control thermocouple is lower than that of the temperature measurement thermocouple, adjusting the connection of two thermocouples, and ensuring that the temperature value of the thermocouple for temperature control in the same repair area is not lower than that of the temperature measurement thermocouple, thereby ensuring accurate adjustment and control of the heating temperature; after the thermocouple is installed and adjusted and measured, the designed flexible heater covers the thermocouple and is adjusted and positioned at the repair part;
5. purifying the atmosphere in an argon protection box; introducing argon gas into the heat treatment protection box for washing to ensure that the oxygen content in the box is lower than 100 PPM; the inside of the protective box is circularly purified, so that the water oxygen content in the box is lower than 50PPM after purification, and a low water oxygen and argon protective processing environment is provided for local heat treatment of large complex aviation titanium alloy structural parts.
6. And (3) carrying out local heat treatment on the repair area of the large complex aviation titanium alloy structural part by adopting a flexible heating device. According to the invention, a high-frequency heating source with the frequency of 20-80kHz is adopted, the oscillation current of the heating source is adjusted through an intelligent temperature controller, the output power is controlled, the temperature is raised through a flexible heater, and a local high-temperature field is generated, so that the heat treatment of the local repair part of the large-scale complex aviation titanium alloy structural part is realized; and setting the temperature rise time, the heat preservation temperature, the heat preservation time and the cooling time of each determined stage of the local heat treatment through the intelligent temperature control box, and starting a power supply after the setting is finished to carry out the local heat treatment on the repair area of the large-scale complex aviation titanium alloy structural component.
The invention has the following advantages:
1. the flexible heater mainly adopts a crawler-type ceramic heater, can be spliced, bent and wound according to the structural characteristics of a repaired workpiece and a repaired part, is tightly attached to the surface of a repair area of the large-scale complex aviation titanium alloy structural component for contact heating, and can simply and effectively realize the heating of the complex structure of the repair area.
2. Based on the optimal arrangement and real-time temperature measurement of the multipoint thermocouples, the heating power is automatically regulated and controlled, the accessibility of local heating temperature is ensured, the reliability of a required heat treatment system is ensured, and the adaptive local heat treatment of the multi-type damage repairing structure can be realized.
3. The heating temperature is regulated and controlled by adjusting the oscillating current of a high-frequency heating source (with the frequency of 20-80kHz) through an intelligent temperature controller, so that the accurate control of the local heat treatment temperature is realized.
4. The argon protection box is adopted to carry out local heat treatment on the large complex aviation titanium alloy structural part under the integral argon protection state, the water oxygen content in the box can be lower than 50PPM after purification, and high-temperature oxidation during local heat treatment is prevented.
5. The flexible heating device can be used for carrying out local heat treatment on the repair area of the large complex aviation titanium alloy structural component, and the heat affected area is small and the deformation is small.
More specifically, as shown in fig. 1, the device for local heat treatment after repair of a large complex aviation titanium alloy structural component comprises a protective gas tank body, a thermocouple 2, a flexible heater 3 and an intelligent temperature controller, wherein the protective gas tank body, the thermocouple 2, the flexible heater 3 and the intelligent temperature controller are commercially available or manufactured according to methods disclosed in the prior art, and can be selected and set by a person skilled in the art according to the prior art. The thermocouple 2 is arranged at a part repairing part and connected with the intelligent temperature controller, the corresponding flexible heater 3 is designed and manufactured according to the shape characteristics of the part repairing area, is tightly attached to the surface of the aerospace large-scale complex part repairing area, wraps the thermocouple 2 and is connected with the intelligent temperature controller, and the aviation titanium alloy large-scale complex structural part is placed in the argon protection box 2.
The thermocouple 2, the flexible heater 3 and the intelligent temperature controller form a flexible heating local heat treatment system. The surface temperature of the workpiece repairing area is detected through the thermocouple 2, the current is adjusted through the intelligent temperature controller, and local heating and heating temperature regulation and control of the casing repairing area are achieved.
According to a formulated flexible heating local heat treatment system, the temperature of the repaired part is detected by adopting the thermocouple 2, the oscillation current is adjusted by an intelligent temperature controller, and the heating rate, the heat preservation temperature, the heat preservation time, the cooling time and the like are controlled.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. The utility model provides a local heat treatment device after large-scale complicated structure spare of aviation titanium alloy is restoreed which characterized in that includes:
the heater is used for heating the repair part of the large-scale complex aviation titanium alloy structural part (4) in a fitting manner;
the temperature sensor is used for detecting the temperature of the repair part of the large-scale complex aviation titanium alloy structural part (4);
and the temperature controller (5) is in communication connection with the heater and the temperature sensor respectively.
2. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural parts according to claim 1, wherein the heater is a flexible heater (3).
3. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural components according to claim 2, wherein the flexible heater (3) comprises a crawler-type ceramic heater or a silicon rubber flexible heater.
4. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural members according to claim 1, wherein the temperature sensor comprises:
the thermocouple (2) is arranged on the surface of the repair part of the large-scale complex aviation titanium alloy structural part (4);
the heater is attached to the surface of the repair part of the large-scale complex aviation titanium alloy structural part (4) and wraps the thermocouple (2).
5. The post-repair local heat treatment device for the large-scale complex aviation titanium alloy structural part according to claim 4, wherein the number of the thermocouples (2) is two, and the thermocouples are a temperature measuring thermocouple and a temperature control thermocouple;
the temperature thermocouple and the temperature thermocouple are arranged on different surfaces of the repaired part of the large complex aviation titanium alloy structural part (4) and are in one-to-one corresponding communication connection with two different interfaces of the temperature controller (5), so that the detection value of the temperature thermocouple is larger than that of the temperature thermocouple.
6. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural members according to claim 1, further comprising:
and the heat insulation layer is used for wrapping the repair part of the large-scale complex aviation titanium alloy structural part (4) and is positioned on the outer side of the heater.
7. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural members according to claim 6, wherein the heat-insulating layer comprises an asbestos heat-insulating layer (7).
8. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural members according to claim 1, further comprising:
and the argon protection box (1) is used for placing the large-scale complex structural part (4) of the aviation titanium alloy, and the heater and the temperature sensor are both positioned in the argon protection box.
9. A local heat treatment method after repairing an aviation titanium alloy large-scale complex structural part is characterized in that the local heat treatment device is adopted for local heat treatment after repairing the aviation titanium alloy large-scale complex structural part according to any one of claims 1 to 8, and the method comprises the following steps:
s1, setting temperature rise time, heat preservation temperature, heat preservation time and cooling time of each stage of local heat treatment through a temperature controller according to the determined heat treatment system after repairing the large-scale complex aviation titanium alloy structural part;
and S2, controlling the operation of the heater through a temperature controller according to the temperature rise time, the heat preservation temperature and the heat preservation time of each stage of the local heat treatment set in the step S1.
10. The method for locally heat treating the repaired large-scale complex aviation titanium alloy structural component according to claim 9, wherein in step S1, the heat treatment schedule for the repaired large-scale complex aviation titanium alloy structural component comprises:
uniformly heating to 600 ℃ in multiple stages according to a preset heating speed, and keeping the temperature for 4 hours; and keeping the temperature for 5min when the temperature is increased to the corresponding preset temperature in each stage.
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| RU2225514C2 (en) * | 2001-04-17 | 2004-03-10 | Юнайтид Текнолоджиз Копэрейшн | Method of making rotor en-bloc with blades (versions), device for local heat treatment and method of repair of blades of said rotor |
| CN106636600A (en) * | 2016-11-09 | 2017-05-10 | 成都发动机（集团）有限公司 | Method for partial heat treatment of aero-engine large part after repair welding |
| CN106680057A (en) * | 2016-12-27 | 2017-05-17 | 中国科学院合肥物质科学研究院 | Nano-level particulate matter supersaturated growth device and control method |
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2022
- 2022-04-13 CN CN202210385607.0A patent/CN114855106A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2225514C2 (en) * | 2001-04-17 | 2004-03-10 | Юнайтид Текнолоджиз Копэрейшн | Method of making rotor en-bloc with blades (versions), device for local heat treatment and method of repair of blades of said rotor |
| CN106636600A (en) * | 2016-11-09 | 2017-05-10 | 成都发动机（集团）有限公司 | Method for partial heat treatment of aero-engine large part after repair welding |
| CN106680057A (en) * | 2016-12-27 | 2017-05-17 | 中国科学院合肥物质科学研究院 | Nano-level particulate matter supersaturated growth device and control method |
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